Monoplane.



.A. MARUCA.

MONOPLANE. APPucAfloN FILED ocT. l7. 1914.

Patented Jul 18, 1916.

3 SHEETS-SHEET I.

A. MAHUCA.

-MONOPLANE.

7 APPLICATION FILED OCT. 17, 19M. I L19L4. I Patented July 18, 1916.

3 SHEETS-SHEET .2.

A. MARUCA.

MO NNNNNN E.

APPLICATION FILED OCT- I7, 1914 Patented July 18,1916

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ANTHONY MARUOA, OF ANITA, PENNSYLVANIA.

MONOPLANE.

I Specification of Letters Patent.

Patented July 18, 1916.

Application filed October 17, 1914. Serial No. 867,150.

I! '0 all (Ir/mm. it may concern:

Be itv known that I, Ax'riioxr MARIL'GA,

a subject of the King of Italy, residing at Anita, in the county of Jefferson and State of Pennsvlvania, have invented certain new and useful Improvements in Monoplahes, of which the following is a specification.

This invention relates to flying machines of the heavier-than-air variety and more specifically relates to that type of aeroplane commonly designated as a monoplane by reason of its single supporting surface.

As a principal object, this invention contemplates the provision of a monoplane which shall be constructed with regard to 'a novel ;l(lil]')ttltl01l of the dihedral angle construction of the supporting surface.

A coord1nate.'ob ect is to incorporate with the novel surface (f the type described warpable wing tips readily controllable by the operator to increase the angle of incidenceof the wing tips iii the well-known manner. 5 v r It is a further object to provide a following tail-plane simultaneously controllable by the steering means for the usual rudder and acting as an auxiliary stabilizing mode in conjunction with the wing tips.

It is an object of equal importance'to provide a specific arrangement of nionoplane of the type described which in addition to embodying the previously mentioned teat'ures will be so constructed as to present the utmost simplicity of design consistent, with its-efficiency and dural'iilityin operation.

The above and additionalob'jects which will become apparent as this explanatory description proceeds,- are accomplished by such means asare illustrated in the accompanying drawings, described in the following specification, and then more particularly pointed out in the claims which are appended hereto and form a part of this application.

- \Vith reference-to the drawings, wherein there is illustrated the preferred embodi-' ment of this invention as it is' reduced to practice, and throughout the several viewsof which like characters of reference designate similar parts: Figure 1 is a front elevation of amonoplane. construct-ed to embrace the particular features of this invention,

- Fig. 2 is a plan view of the-matter shown in Fig. 1, a small portion being necessarily broken away, Fig. 3 IS a s de elevational view, and Fig. 4 is a detail perspective view of the following tail. plane removed from the \plane. Fig. 5 is a detail view of the operating lever for operating the wing planes.

In modern aeroplane design, attention is chiefly directed to rendering the machines stable in divers air currents, and the means of attalnlng the desired stability are usually classified under two heads, first the design and arrangement of the sustaining surfaces which result in a certain amount of inherent stability and; secondly the construction of movable surfaces whereby a controllable stability is effected. These considerations are pertinent to this invention which is chiefly concerned in producing an extremely stable monoplane and to this end has undertaken the improvements in aerofoil design as well as aileron and wing tip arrangement to be hereinafter disclosed.

Considering first well known aerofoil structure, what is known as the dihedral angle or V-form of monoplane such as has been experimented with in the Antoinette type has been found to possess certain advantages particularly when the machine is volplanmg, and certain authorlties pronounce it an improvement as regards sustaining power. Certain disadvantages how-' ever, have arisen in this type due to the great strain upon the wing tips which has often resulted in the buckling of the latter upon the giving way of thelower ties and the consequent destruction of the machine. It is therefore proposed by this invention to incorporate the advantages of this type of aerofoil construction while doing away with its faults in the manner to immediately appear.

In Figs. 1, and 2, there is shown an aerofoil comprising acentral portion formed of the two inwardly and upwardly arching planes 5 6 whose meeting line lies .in' the central longitudinal vertical plane of the 'machine so that a somewhat arcuate dihedral angleis formed which is the reverse of that usually employed where as is Well known the planes incline downwardly and inwardly to ameeting edge. The surfaces of the planes are smaller than those usually pose to be hereinaftermentioned. The span webs 7 support the' mentioned planes and in addition carry a pair of aerofoils 8, one cf which adjoins each of the mentioned planes and 6 at their base line and is there maintained by ribs 9. Wing tips 10 of substantially the same size as the arched planes and similarly increasing in width with upward progress are maintained in juxtaposition to the outer edges of the planes 8 by the pairs of outrigger rods.11 which also serve to support the extremities of the webs 7 by means of the metallic angle plates 12 which latter are formed with an intermediate step portion and terminal wings, the former sustaining the webs 7 and one each of the latter connectedrespectively to the wings 1O and rods 11. The connection between the forward plates 12 and the mentioned wing tips is preferably slightly loose in order to provide for the warping of the forward edges of the wing tips which is accomplished by means of a flexible connection 13 operable by the monoplane pilot to act upon the projecting end 14 of the warping lever 15 carried along the lower edge of each wing tip. Pulleys 16 are arranged upon the frame members 7 in order to permit of a normal pull by the connections 13 upon the lever ends 14. From thence these connections run to eye bolts 17 in order to be horizontally directed to the ends of the control lever 18 which is pivoted transverse on the chassis members 19 immediately below a drivers seat 20 also supported on the members 19 in order that'the said control lever may be operated by the feet or knees of the pilot. As a means for preventing movement of the rear portion of the wing .tips when it is intended to warp the forward edge, rigid stays 21 are provided supported at one extremity by the ribs 9 and connected at the other to the upper rear end of each wing as a reliable prevention of a buckling ,on the part of these aerofoil members. A

the construction of the various suitable fabric 23 may be horizontal fuselage members 27 which are also connected at their front extremities with the frame rods 19 by means of struts 28 and which support intermediately the engine 29 and fuel tank 30, the former being provided with a cased drive 31 having the ribs 24 in any wettsecured at the extremity thereof the pro.- peller 32 positionedin the usual forward situation common to monoplanes.

Chassis members 33 extend similarly from the members 27 in a diagonal manner to sup port the rear wheels 34 being braced adacent thereto by a suitable means 35.

Lower fuselage frame members 36 converge rearwardly to support with. the similar members 27 the rudder post 37 to which is pivoted the rudder or tail fan 38 in suitable hinge brackets 39. As a controlling means for the rudder, there is provided a flexible connection 40, each end of which is secured as at 41 to opposite sides of the rudder and centrally thereof, the said connections extending'laterally from their fastening point tothe tail by traveling over pulleys 42 mounted in the end laterally directed braces ,43 secured to the upper fuselage-members 27 and further braced by the transverse stay 44. Leading forwardly from the pulleys 42 the connections 40 pass through theeye bolts 17 to pulleys 45 carried on the extremities, of a pivoting pin which mounts the control lever 46. This lever 46 has a longitudinal swaying movement and is bifurcated at its upper end in order to receive the tail controlling wheel 47 which is circumferentially grooved to receive the central bight of the flexible connections 40'. v

The forward and rearward movement of the control lever is designed for operating the following tail plane 48 bymeans of the flexible connections 49 secured to the lever on opposite sides of the pivoting-point and passing rearwardly thence to respective pulleys 50 carried by the cross brace 44 and the tail post 37 to vertically direct the connections 49 to a common point of fastening in the retaining eye 51 carried by the tail plane 48. This tail plane consists of a pair of substantially triangular lateral wing portions 52 formed similarly to the described planes and connected by a like metallic central web The forward or entrant portions'of this tail plane are slightly cambered and reinforced by rod braces 54 which are held taut by struts 55.- Pivotingplates 56 are formed with suitable eyes 57 adapted to receive the transverse pin 58 which is supported by uprights 59 secured to andbracing the fuselage members 27 and 36 in the manner indicated in Fig. 3.

The foregoing description covers a sufficiently detailed disclosure of the present in vention to permit recognition of the novel departure from customary monoplane construction herein contained. It will be noted that what has been termed side slip-Which may be briefly explained as that tendency of the air to take the path of least resistance upon encountering an obstacle, which results in. an attempt to escape laterally as well as over the forward and rear edgesmay be .the heading of automaticstability.

known to necessitate discussion in this art and both being simultaneously controllable,

by the pilot without his being forced to remove his hands from the rudder control 47.

It is to be particularly noted that a close association exists between the arrangement of the warpable wing tips and the structure of the aerofoil permitting the wing portions 10 to partake of the nature of both auto-, matic and controlled stabilitya novel feature of unquestioned advantage in the structure of modern flying machines.

While in the foregoing however, there has thus been illustrated in the drawings, and described in the specification, such combination and arrangement of elements as constitute the preferred embodiment of this invention, it is desired'to emphasize the fact that such minor changes in the matters of proportion and. degree may be made in later adaptations of this device as shall not alter the spirit of the invention as defined in the appended claims.

lVhat is claimed is:

1. In an aeroplane, arched main planes forming a dihedral angle, intermediate horizontal planes, and outwardly inclined planes carried at the endsof said intermediate planes, the width of said first and last planes increasing upwardly. v

2. In an aeroplane, an aerofoil including arched central planes, intermediate planes connected to sa1d arched planes at their bases, outwardly inclined wing planes at the ends of said intermediate planes, a lever extremity carried by the forward edge of each of saic wing planes, means for bracing the rearward edge of each of said wing planes, and means connecting with said lever extremities for warping said wing planes.

3. In an aeroplane, an aerofoil structure including spaced webs, arched planes .cen-

trally supported upon said webs, wing planes carried at the extremities of said webs in outward inclination, an intermediate horizontal plane resting directly upon said webs between each of said arched planes and a wing plane, a lever extremity carried by the forward edge of each wing plane, a

- brace extending from one of said webs to the rearward extremity of each of said Wing planes, and means connecting with said lever extremities for manual Warping of'the forward 'edgeo'f said wing planes.

4. In an aeroplane, an aerofoil includingarchedcentral planes, ntermediate planes connected to'said arched planes at their bases, outwardly inclined wing planes at the ends of said intermediate planes, a lever extremity carried by the forward edge of each of said wing planes, means for bracing the rearward edge of each of said wing planes, means connecting with said lever extremities for warping said wing planes, and means coordinating the action of said wing planes when warped.

5. In an aeroplane, an aerofoil structure including spaced. webs, arched planes centrally supported upon saidfwebs, wing planes carried. at the extremities of said webs in outward inclination, intermediate planesv resting directly upon said webs be tween each of said arched planes and a wing plane, a leverv extremity carried by the forward edge of each wing plane, a brace extending from one of said webs to the re arwardextremity of each of said wing planes, means connecting with sald lever extrcuu; ties for manual warping of the forward edge of said wing planes, and means cofl ordinating the action of said wing planes when walrped.

(i. In an aeroplane, a plane supporting structure including reaiwvardly converging fuselage members in pairs, means bracing said members, webs transversely supported. by the uppermost pair of said members, an aerofoil-structure including arched planes centrally supported upon said webs, wing planes supported at the extremities of said webs, an, intermediate plane between each arched plane and wing plane, an operating lever pivoted "to one pair of said fuselage members, a lever extremity prolonged upon the forward edge of each of said wing planes, a brace between one of said webs and the rearward edge of each wing plane, and flexible connections between each lever extremity and said operating lever for warping the forward edge of such planes.

7. In an aeroplane, a plane supporting structure including rearwardly converging fuselage members in pairs, means bracing said members, webs transversely supported by the uppermost pair of said members, an aerofoil structure including arched planes centrally supported upon said webs, wing planes supported at the extremities of said webs, an intermediate plane between each arched plane and an end plane, an operating lever pivoted to one pair of said fuselage members, a lever extremity prolonged upon i v a tailplane centrally pivoted to a pairof said struts, a

planes at poants opposite to the lever prolongatio'n for-coordinating the warping action of such planes.

8. In an aeroplane, a fuselage including members, rearwardly converging in pairs, struts bracing said members, frame members connected to both pairs of said members, a lever pivoted for longitudinal movement between said frame members, a wheel rotatably mounted in said lever, a tail-plane pivoted to two ofsaid struts I central edge, pulleys carried at the rear of said fuselage, and a flexible connection attached to said tail-plane passing above and below the pivotal axis of the same, over the respectivepulleys and thence forward to be connected to opposite sides of said lever from the pivot point thereof.

9. In an aeroplane, a fu'selage including frame members rearwardly converging in pairs, struts bracing said members, a pair of chassis ,frame members connected to each pair of said fuselage members, a rudder post carried by said first frame members, a rudderhorizontally movable on said post,

lever pivoted between said chassis frame members, a. wheel rotatably mounted within said lever, flexible connections oppositely leading from said tail-plane to opposite points of said lever, and similar" fiexible connections leading from opposite sides of said rudder and having a bight portion thereof receivable over said wheel.

at its forward 10. In an aeroplane, a fuselage including frame members converging rearwardly in pairs, a rudder post supported by said frame members, chassis frame members connected to each pair of said fuselage frame members, a lever pivoted between said chassis frame members, a wheel rotatably chassismembers adjacent said first-men tioned lever, flexible connections between said lever, extremities on the wing planes and said operating lever, a tail-piece pivj0tally mounted at the rear of the fuselage, flexible connections between said tail-plane and said first-mentioned lever, a rudder, flexible connectionsbetween said rudder and said wheel having a central bight'thereof receivable thereover, and a flexible connection between the forward edges of said wing planes for coordinating warping action thereof. 7

In testimony whereofl affix my signature in presence of two witnesses.

ANTHONY MARUCA.

Witnesses:

EARL'J. ,WEIS, EMERY R. MILLER.

Copies of this patent may be obtained for five cents each, by addressing the fGommissioner of Patents,

' I Washington, D. 0. I 

